A turbine disk has an at least partially radially-extending first portion. An at least partially axially-extending circumferential flange has a root connecting the flange to the first portion. The flange extends to a rim and has a plurality of pairs of first and second weight-mounting fastener apertures. A plurality of first recesses are provided in the rim, each position between an associated first and second aperture of an associated one of the aperture pairs. A plurality of second recesses are provided in the rim each positioned between an adjacent two of the pairs.
|
10. A method for remanufacturing a turbine disk, the disk initially comprising:
an at least partially radially-extending first portion; and
an at least partially axially-extending circumferential flange having:
a root connecting the flange to the first portion;
a rim;
a plurality of pairs of first and second weight-mounting fastener apertures; and
a plurality of first recesses in said rim, each positioned between an associated first aperture of an associated first one of said pairs and an adjacent associated second aperture of an associated second one of said pairs,
the method comprising:
broadening said first recesses.
21. A method for remanufacturing a turbine disk, the method comprising:
providing a disk initially having:
an at least partially radially-extending first portion; and
an at least partially axially-extending circumferential flange having:
a root connecting the flange to the first portion;
a rim;
a plurality of pairs of first and second weight-mounting fastener apertures; and
a plurality of first recesses in said rim, each positioned between an associated first aperture of an associated first one of said pairs and an adjacent associated second aperture of an associated second one of said pairs and broadening said first recesses.
1. A turbine engine disk comprising:
an at least partially radially-extending first portion; and
an at least partially axially-extending circumferential flange having:
a root connecting the flange to the first portion;
a rim;
a plurality of pairs of first and second weight-mounting fastener apertures;
a plurality of first recesses in said rim, each positioned between an associated first and second aperture of an associated one of said pairs; and
a plurality of second recesses in said rim each positioned between an associated first aperture of an associated first one of said pairs and an associated second aperture of an associated second one of said pairs, adjacent said first one of said pairs.
20. A method for remanufacturing a turbine disk, the disk comprising:
an at least partially radially-extending first portion; and
an at least partially axially-extending circumferential flange having:
a root connecting the flange to the first portion;
a rim;
a plurality of pairs of first and second weight-mounting fastener apertures; and
a plurality of first recesses in said rim, each positioned between an associated first aperture of an associated first one of said pairs and an adjacent associated second aperture of an associated second one of said pairs,
the method comprising:
broadening said first recesses at least at a longitudinal location between axes of the weight-mounting fastener apertures.
14. A turbine engine disk comprising:
an at least partially radially-extending first portion; and
an at least partially axially-extending circumferential flange having:
a root connecting the flange to the first portion;
a rim;
a plurality of pairs of first and second weight-mounting fastener apertures;
a plurality of first recesses in said rim, each positioned between an associated first and second aperture of an associated one of said pairs; and
a plurality of second recesses in said rim each positioned between an associated first aperture of an associated first one of said pairs and an associated second aperture of an associated second one of said pairs, wherein the second recesses are deeper than the first recesses.
5. A method for remanufacturing a turbine disk, the disk initially comprising:
an at least partially radially-extending first portion; and
an at least partially axially-extending circumferential flange having:
a root connecting the flange to the first portion;
a rim;
a plurality of pairs of first and second weight-mounting fastener apertures; and
a plurality of first recesses in said rim, each positioned between an associated first aperture of an associated first one of said pairs and an adjacent associated second aperture of an adjacent associated second one of said pairs,
the method comprising:
machining a plurality of second recesses in said rim each positioned between an associated first and second aperture of an associated one of said pairs.
17. A turbine engine disk comprising:
an at least partially radially-extending first portion; and
an at least partially axially-extending circumferential flange having:
a root connecting the flange to the first portion;
a rim;
a plurality of pairs of first and second weight-mounting fastener apertures;
a plurality of first recesses in said rim, each positioned between an associated first and second aperture of an associated one of said pairs; and
a plurality of second recesses in said rim each positioned between an associated first aperture of an associated first one of said pairs and an associated second aperture of an associated second one of said pairs, wherein along inboard and outboard surfaces of the flange at an axial location of said apertures, the second recesses are broader than the first recesses.
19. A method for remanufacturing a turbine disk, the disk comprising:
an at least partially radially-extending first portion; and
an at least partially axially-extending circumferential flange having:
a root connecting the flange to the first portion;
a rim;
a plurality of pairs of first and second weight-mounting fastener apertures; and
a plurality of first recesses in said rim, each positioned between an associated first aperture of an associated first one of said pairs and an adjacent associated second aperture of an associated second one of said pairs,
the method comprising:
machining a plurality of second recesses in said rim each positioned between an associated first and second aperture of an associated one of said pairs; and
trimming said rim so as to bring the rim closer to axes of the first and second weight-mounting fastener apertures.
3. The disk of
4. The disk of
a first weight secured to the disk by: a first fastener engaging said first fastener aperture of an associated one of said pairs; and a second fastener engaging said second fastener aperture of said associated one of said pairs.
6. The method of
removing the disk from a turbine engine before said machining.
8. The method of
trimming said rim so as to bring the rim closer to axes of the first and second weight-mounting fastener apertures.
9. The method of
removing weights from the disk before the machining; and
installing weights on the disk after the machining.
11. The method of
12. The method of
removing weights from the disk before the broadening; and
installing weights on the disk alter the broadening.
13. The method of
15. The disk of
16. The disk of
a first weight secured to the disk by: a first fastener engaging said first fastener aperture of an associated one of said pairs; and a second fastener engaging said second fastener aperture of said associated one of said pair.
18. The disk of
a first weight secured to the disk by: a first fastener engaging said first fastener aperture of an associated one of said pairs; and a second fastener engaging said second fastener aperture of said associated one of said pairs.
|
(1) Field of the Invention
This invention relates to balancing of turbine rotors by the addition of weights, and more particularly to rotor flanges to which the weights are mounted.
(2) Description of the Related Art
The dynamic balancing of turbine rotors is a well-developed art. Each rotor may have, at one or more longitudinal locations, a circumferential array of mounting features permitting the installation of one or more balance weights.
It is known, for example, to balance a rotor by using a computer-controlled apparatus to spin the rotor about its rotational axis and measure the parameters of rotational displacements associated with imbalance. Based upon these measurements, the computer outputs an identification of a particular combination of balance weights to balance the rotor. Specifically, the computer may identify particular weight masses to be installed at one-to-all of the individual mounting locations defined by the mounting features.
Accordingly, one aspect of the invention involves a turbine disk having an at least partially radially-extending first portion. An at least partially axially-extending circumferential flange has a root connecting the flange to the first portion. The flange extends to a rim and has a plurality of pairs of first and second weight-mounting fastener apertures. A plurality of first recesses are provided in the rim, each position between an associated first and second aperture of an associated one of the aperture pairs. A plurality of second recesses are provided in the rim each positioned between an adjacent two of the pairs.
Other aspects of the invention relate to remanufacturing a turbine disk. The disk initially has a plurality of recesses in its balancing flange rim, each positioned between a first aperture of one aperture pair and adjacent second aperture of an adjacent aperture pair. The method may involve broadening such recesses. The method may involve adding a plurality of additional recesses in the rim, each positioned between first and second mounting apertures of an associated mounting aperture pair. The method may also involve longitudinally trimming the rim.
The details of one or more embodiments of the invention are set forth in the accompanying drawings and the description below. Other features, objects, and advantages of the invention will be apparent from the description and drawings, and from the claims.
Like reference numbers and designations in the various drawings indicate like elements.
In the exemplary embodiment, the rear hub 28 has a frustoconical web 40 extending aft and radially inward from a junction with the rear blade disk 26 to a flange 42 for mounting to a high spool shaft (not shown). The rear hub 28 has a balance flange 50 extending generally longitudinally aft from the web 40. The exemplary flange has inboard and outboard surfaces 52 and 54 and extends from a relatively thick root 56 at the web 40 to an aft rim 58. A relatively thin distal or aft mounting portion 60 extends to the rim 58 and is provided with mounting apertures (discussed below) for the securing of weights 62 by means of fasteners 64 (e.g., rivets or threaded fasteners). In the exemplary embodiment, the flange inboard surface 52 has a smooth continuously curving transition to the outboard/aft surface of the web 40 and smoothly extends to a distal longitudinal portion along the mounting portion 60. The flange outboard surface 54 has a shoulder or step 70 at the fore/proximal end of the mounting portion 60, extending generally longitudinally fore and aft of the step. An intermediate portion 72 extends forward from the shoulder 70 with inboard and outboard surfaces initially parallel and then transitioning as described above. At the exemplary root 56 the outboard surface defines a slight channel 74 which facilitates machining of the surface 54.
The flange 150 may be remanufactured in one or more ways to more closely resemble the flange 50. The recesses 186 may be machined to broaden them and make them more blunt. The rim may be trimmed by machining to longitudinally shift the broken annular portion 188 forward. The second plurality of the recesses can be machined between adjacent apertures of each pair.
In an exemplary implementation, a flange radius along the outboard surface of the mounting portion 60 is 9.58 inches, a thickness of the mounting portion is 0.131 inches, a length of the mounting portion 60 is 0.5375 inch, and there are twenty pairs of mounting apertures. The mounting apertures have a nominal diameter of 0.11 inch, with a diameter at the chamfer of 0.16 inch. The separations S1, S2 and S3 are 0.719, 0.786, and 0.117 inch. The longitudinal spans L3 and L4 are 0.115 and 0.075 inch. The radius R1 is 0.21 inch and the separation S4 is 0.025 inch. The radii R2 and R3 are 0.575 and 0.13 inch. The widths W1, W2, and W3 are 0.417, 0.490, and 0.478 inch. In the exemplary embodiment the depth and breadth of the recess 86 serves to reduce weight and hoop stresses at the circumferential ends of the weight mounting areas. The recesses 84 serve primarily for weight reduction as hoop stress reduction is not as great a concern within individual weight mounting areas. The partial circle shape of the recesses 84 reflects ease of machining (e.g., through use of simpler, less expensive, and/or more robust machining cutter and/or reduced use of the cutter). Although potentially advantageous from a weight reduction point of view, the benefits of making the recesses 84 similar to the recesses 86 might not be worth the additional manufacturing costs.
One or more embodiments of the present invention have been described. Nevertheless, it will be understood that various modifications may be made without departing from the spirit and scope of the invention. For example, the principles may be applied to various turbine configurations. Accordingly, other embodiments are within the scope of the following claims.
Patent | Priority | Assignee | Title |
10697300, | Dec 14 2017 | RTX CORPORATION | Rotor balance weight system |
10774678, | May 04 2017 | Rolls-Royce Corporation | Turbine assembly with auxiliary wheel |
10865646, | May 04 2017 | Rolls-Royce Corporation | Turbine assembly with auxiliary wheel |
10968744, | May 04 2017 | Rolls-Royce Corporation | Turbine rotor assembly having a retaining collar for a bayonet mount |
11326454, | Dec 14 2017 | RTX CORPORATION | Rotor balance weight system |
11448081, | Oct 18 2019 | RTX CORPORATION | Balanced circumferential seal |
11578599, | Feb 02 2021 | Pratt & Whitney Canada Corp | Rotor balance assembly |
11821321, | Oct 18 2019 | RTX CORPORATION | Balanced circumferential seal |
7309211, | Dec 18 2004 | Rolls-Royce plc | Balancing method |
7364402, | Apr 29 2005 | SAFRAN AIRCRAFT ENGINES | Turbine module for a gas turbine engine |
7912587, | Jul 25 2007 | Pratt & Whitney Canada Corp | Method of balancing a gas turbine engine rotor |
8025483, | Oct 24 2006 | SAFRAN AIRCRAFT ENGINES | Balancing system for turbomachine rotor |
8353670, | Jul 30 2009 | Pratt & Whitney Canada Corp. | Axial balancing clip weight for rotor assembly and method for balancing a rotor assembly |
8506253, | Aug 19 2009 | Pratt & Whitney Canada Corp. | Balancing apparatus for rotor assembly |
8631578, | Oct 01 2009 | Pratt & Whitney Canada Corp. | Radial balancing clip weight for rotor assembly |
8727719, | Nov 07 2008 | SAFRAN AIRCRAFT ENGINES | Annular flange for fastening a rotor or stator element in a turbomachine |
8851847, | Nov 15 2010 | MTU AERO ENGINES GMBH, A COMPANY OF GERMANY | Rotor for a turbo machine |
8888458, | Mar 12 2012 | RTX CORPORATION | Turbomachine rotor balancing system |
8984940, | Apr 04 2012 | Elliot Company | Passive dynamic inertial rotor balance system for turbomachinery |
9039351, | May 29 2008 | SAFRAN AIRCRAFT ENGINES | Annular flange for fastening a rotor or stator element |
9169730, | Nov 16 2011 | Pratt & Whitney Canada Corp. | Fan hub design |
9810076, | Nov 16 2011 | Pratt & Whitney Canada Corp. | Fan hub design |
Patent | Priority | Assignee | Title |
4220055, | Sep 23 1977 | Societe Nationale d'Etude et de Construction de Moteurs d'Aviation | Device to balance a rotor |
4270259, | Mar 15 1979 | Twenty-First Century Research Corporation | Method and apparatus for rebuilding advance weights |
4803893, | Sep 24 1987 | United Technologies Corporation | High speed rotor balance system |
5369882, | Feb 03 1992 | General Electric Company | Turbine blade damper |
Executed on | Assignor | Assignee | Conveyance | Frame | Reel | Doc |
Feb 10 2003 | United Technologies Corporation | (assignment on the face of the patent) | / | |||
Feb 10 2003 | ALLAM, MAHDY A | United Technologies Corporation | ASSIGNMENT OF ASSIGNORS INTEREST SEE DOCUMENT FOR DETAILS | 013772 | /0593 | |
Apr 03 2020 | United Technologies Corporation | RAYTHEON TECHNOLOGIES CORPORATION | CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874 TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001 ASSIGNOR S HEREBY CONFIRMS THE CHANGE OF ADDRESS | 055659 | /0001 | |
Apr 03 2020 | United Technologies Corporation | RAYTHEON TECHNOLOGIES CORPORATION | CHANGE OF NAME SEE DOCUMENT FOR DETAILS | 054062 | /0001 |
Date | Maintenance Fee Events |
Aug 15 2005 | ASPN: Payor Number Assigned. |
Sep 18 2008 | M1551: Payment of Maintenance Fee, 4th Year, Large Entity. |
Sep 28 2012 | M1552: Payment of Maintenance Fee, 8th Year, Large Entity. |
Oct 27 2016 | M1553: Payment of Maintenance Fee, 12th Year, Large Entity. |
Date | Maintenance Schedule |
May 17 2008 | 4 years fee payment window open |
Nov 17 2008 | 6 months grace period start (w surcharge) |
May 17 2009 | patent expiry (for year 4) |
May 17 2011 | 2 years to revive unintentionally abandoned end. (for year 4) |
May 17 2012 | 8 years fee payment window open |
Nov 17 2012 | 6 months grace period start (w surcharge) |
May 17 2013 | patent expiry (for year 8) |
May 17 2015 | 2 years to revive unintentionally abandoned end. (for year 8) |
May 17 2016 | 12 years fee payment window open |
Nov 17 2016 | 6 months grace period start (w surcharge) |
May 17 2017 | patent expiry (for year 12) |
May 17 2019 | 2 years to revive unintentionally abandoned end. (for year 12) |